Aeroplane.



P. H. SMITH.

AEROPLANE.

APPLICATION FILED 00'1.7, 1913.

1, 1 1 0,355. Patented Sept. 15, 1914.

3 SHEETS-SHEET 1.

P. H. SMITH.

AEROPLANE.

APPLICATION FILED OQT.7, 1913.

1,1 1 0,355, Patented Sept. 15, 1914,-

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P. E. SMITH.

ABROPLANE.

APPLIGATION FILED 0c T.7, 1913.

1,1 10,355. Patented Sept. 15, 1914 3 SHEETS-SHEET 3.

UNITED STATES PATENT oFFIoE.

PHILIP H. SMITH, or PAWLING, NEW YORK.

AEROPLANE.

Specification of Letters Patent. Patented S t 15 1914 Application filedOctober '7, 1913. Serial No. 793,790.

To all whom it may concern:

Be it known that I, PHILIP H. SMITH, citizen of the United States, and aresident of Pawling, Dutchess county, State of New York, have inventedcertain new and useful Improvements in Aeroplanes, of which thefollowing is a specification.

' The object of my inventionis to prevent the precipitate descentofan'aeroplane in W ing to my invention, and presumably travel ing ahorizontal dlrection or substantially so; Fig. 2, a similar view showingthe biplane tilted at an angle of'forty" fivedegrees and the auxiliarysafety plane in independent;

action; Fig. 3, is a top view of my auxiliary safety plane; Fig. 4, isa'sectional elevation upona larger scale, of means for controlling myauxlhary safety-plane, the latter being represented 1n its lowest ornormal positlon and adjacent parts only of the biplane being shown; Fi5, is a section taken upon plane 5-'5 Fig. 4, looking downward; Fig. 6,is a top vlew of the auxillary safety plane rudder expanded; Fig. 7, 1sa view of the auxiliary safety plane released and at the top of themast; Fig. 8, a like view illustrating the relocking of the auxiliarysafety plane prior to its descent into normal position; Fig. 9, 1s adetail of means for limiting the play of the auxiliary safety plane;Fig. 10, a top view with the parts in the positions shown in Fig; S,partly broken away; Fig. 11, is a sectional elevation upon a largerscale of the upper extremity of the mast illustrating means foreffecting the parallelismof the auxiliary safety plane withrelation tothe fixed plane or planes, the lifting pawlbeing shown in its highestposition; Fig. 12,'is a similar View showing the lifting tion. I

In Figs. 4, 7 and 8 the axis 8 of the auxpawl in its lowest posiiliarysafety plane ss, is shown in section,-

the near half of the plane being omitted.

I have herein shown and described mv invention as applied to a biplane,although it is applicable to a monoplane or any conceivable form ofaeroplane, as may be found most expedient, so that I do not limit myselfto the identical form and construct1on of parts herein shown, sincevarious modifications in detail may be resorted to without departingfrom the spirit and intent of my invention in this respect.

WVith this understanding A, represents symbolically an aeroplane of anyordinary or well known construction provided with the parallel planesat, a, and rear controla the motor, propellor'and other details beingomitted.

M is a tubular mastsupported on the main frame-work of the apparatus atright angles to the fixed planes a a,said mast being positionedcentrally and forward,preferably in close proximity and to the rear ofthe seat of theaviator.

1 Normally my auxiliary safety plane 8,8, occupies aposition parallel toand above the upper fixed plane a, as shown in'Figs. 1 and i and beingnormally locked in such position constitutes essentially a supplementalplane of maintenance acting in conjunction withthemain plane or planesbelow'to sus tain'the aeroplane in its flight." Hence, if

used on a biplane it practically gives the effect, under normalconditions, of a triplane; or if used on a monoplane it converts thelatter in some respects, as for normal flying, into abip1ane,thesuperficial area of auxiliary safety plane 8, 8, being of course maderelatively proportionate in order to attain the results desired' Underadverse conditions of flight however the main function of the auxiliaryplane 8, s, is to render the aeroplane self-righting and safe inrecovering or descent. Thus in case of motor failure,'-the breakage ofother parts, or loss of control for any reason, the release of theauxiliary safety'planes, s, obviates all dan ger ofheadlong descent,turning over or collapse, by allowing said auxiliary plane toautomatically adapt itself to the air pressure in such manner as to turnthe aeroplane to face the wind pressure, thereby retarding descent andenabling the aviator to regain control of the apparatus. 4 I

To this end I secure my auxiliary safety plane 8, s, to apivotal axis 8,which is longitudinally parallel to the fixed plane a below, but whichunder certain conditions is free to turn within prescribed limits sothat the said auxiliary safety plane 8, s, when free may adapt itself towind pressure under the guidance and control of a fixed rudder 9,attached to the frame F. This frame F, comprises an upper sleeve f, anda lower sleeve f, both slidably and rotatably mounted upon thecylindrical mast M,said sleeves f, and f being connected with andaffording support for the bracket members 7, f and 7' 7" respectively.Upon the bracket members f 7' the axis 3, of the auxiliary safety plane8, s, is mounted in bearings s, 8, while the rear bracket mem-.

bers 7, f support the rudder r, and the rock lever b, which latter ispivotally attached'as at 7". A stop 6, on the bracket member f limitsthe motion of the rock lever b, in one direction; and a pressure spring5 interposed between the lower part of said rock lever 12 and the sleevef tends constantly to thrust and maintain said lever in contact withsaid stop Z), as shown in Figs. 7 and 8, in which position the shoulder6* on the lever I), is adapted to engage with and support the end of thearm 8 attached rigidly to the axis 8 of the auxiliary plane .9, s. XVhen the auxiliary plane 8, s and frame F descend to the lower normalposition the lower end of the lever 1) contacts with a cam surface 0,thereby rocking the lever Z) against the resistance of the pressurespring 5 as shown in Fig. 4 and thus releasing the arm 8 s is a bolt armalso rigidly secured to the axis 3' of the auxiliary plane .9, s, and

formed at its lower extremity with a shoulder 5*, for engagement with aspring bolt cl, when the frame F is in its lowest position as shown inFig. &,the two armss and 5 extending at right angles to each other orsubstantially so.

A spring 8, attached at one end to the arm 8 and at the other to thesleeve f, tends constantly to depress the arm 8 and to release the arm 3from the spring bolt (Z, and to counteract this tendency, and to lockthe frame F in its lowest position, another spring bolt 6, or equivalentmechanical ex-v pedient is provided, to be retracted either manually asby the handle 6, or automatically when the aeroplane assumes a dangerousinclination'by means of the gravity re lease G. This gravity release G,consists of a weighted pendulum g, suspended from a universal joint gand provided with cross arms 9 connected by cords g or equivalent means,with the. retractor 9 as shown in Fig. l,the slack of the connections'gbeing suflicient, say, to allow ofythe inclination of the aeroplane toany degree less than 45,

the top of the mast.

without causing the gravity release G to retract the bolt 6.

The parts being in the normal positions shown in Fig. &, the withdrawalof the bolt 6, causes the spring .9 acting upon the arm 8 to incline theauxiliary safety plane 3, s, at an angle with relation to the fixed ormain plane a, or planes a, a, and this degree of inclination may belimited, for instance, by a stop 71, consisting of a bent arm secured tothe axis 5 and arranged to contact with a member f of the frame F, so asto limit the divergence of the auxiliary plane 5, s, to say, an angle of45 as related to the main plane or planes. By making this stop arm h,adjustable upon the axis 8, as by a set screw it, as indicated in Fig. 9it is obvious that this degree of divergence of the auxiliary plane s,s, may be regulated and limited as desired; and by the use of a similarstop if, the parallelism of the planes may be attained with accuracy.

The efiect of-the release of the auxiliary safety plane 8, s, is tocause it, under the control of the rudder 1", to present resistance tothe air pressure, and this resistance causes the frame F to slide up themast Muntil the upper collar f, contacts with the cap m, at Hence theauxiliary plane 8, s, acting through the mast as a lever, tends todeflect the aeroplane from itsdownward course and to bring its fixedmain plane or planes again into action in alinement with the airpressure or substantially so, so as to sustain the apparatus more orless in its descent; if not to bring it again under the control of theaviator, for even if failing in this latter respect the auxiliary plane.9, 8, if made ofappropriate superficial area will divert the aeroplanesufficiently from a head-long vertical course to cause it to describe acurve and descend in comparative safety. The mast M not only thus actsas a lever to apply the resistance afforded by the released auxiliaryplane s, s, but it also serves as a track or guide to remove theauxiliary plane from the immediate vicinity of the fixed plane below, toafford freedom of action and available air pressure or res stance.Furthermore the frame F,

-when released from the lower normal positlon shown in Fig. 4, 18 freeto rotate upon all contingencies of accident and disaster,

and to counteract all possible tendency to fall backward or tail-on, Iform the rear portion of the rudder 1', in two sections 1*,

1", hinged to the main portion 9, so that in case of back action orpressure the said rear sections 1", 1*, will be spread apart temporarilyagainst the stops r W, as shown-in Fig. 6, thereby causing the frame Fto swerve'to one side or the other and so to bring the auxiliary plane8, 8,130, faceqthe wind and right the aeroplane.

When the auxiliary plane 3, s, is used temporarily. as an adjunct orsupplementary I means of control, as during gliding, exhibiplane and itsframe willsettle by gravity tion maneuvers 810., or where the'auxiliaryplane has been usedto counteract unfavor able atmospheric conditions andit is desir: able to restore said auxiliary plane and its frame to thenormal position and relationship shownin Figs. 1 and 4, this may beaccomplished by again bringing said auxiliary plane .9, 8, intoparallelismwithlthemain plane or planes, underwhich conditions theauxiliary into said normal position. To this end I provide aplanessettingdevice in the upper part of the mast Mconsistingessentially of: a spring pawl or lifter i, pivotallymountedupon a traveling block'or carrieri', situated within the .mast. Thealinement of this carrier a" maybe provided for in any suitableor-desired manner. Asshowniin the drawthe rotation of the. carrier z";

.12. Attached to the lifting pawl 2', isa cord or equivalent j,passingovena pulley 7" mounted in the upper end of the mast, and downthrough the latter to. a pulley 1 j mounted in an opening in the lowerpart of the mast belowthe fixed plane a, as shown in Fig. 4, from whichopening and pulley j, the cord 7', may be led over anotherpulley 7' somounted as to bring the handle j into convenient proximity to theaviator. Supposing the carrier 71 to be in the lowest position as inFig.12 and the auxiliary plane s, 8, and its frame F to be at the top ofthe mast M and held thereby air pressure due to the inclination of theauxiliary plane 8, 8, if the cord 7', is pulled by means of-the handleit will turn the lifting pawl i, against the resistance of the spring 6until the point i of saidlifting pawl projects through the slot 472/ andwill raisethe carrier i into" the position shown in Fig. 11,the point iof the lifting pawl i,in its upward journey encountering the undersideof thearms and raising it into the position'shown in Fig. 8 againstthe resistance of the spring .9 As the arm 8", is thus raised its endencounters and pushes back the lever b,-against the resistance of thespring 6 which latter when safety." r

the end of theflever, has passed the shoulder 6 forces said shoulder?)under. the end of said arm 8 thereby locking the auxiliary plane s, s,parallel inposition to the fixedv plane at, below, and also bringing thearm 8 into position for engagement with the spring bolt d. The aeroplanebeing presumably,

sailing against and at rightanglesto-the wind pressure, the frame Funder the guidance of the rudder 9, upon the release of the. pull cord7', will descend by gravity in aline-.

ment or substantially so with the boltid, and cam 0, below, and toinsure an accurate register and engagement of thepartsI pre fer to makethe lower portion of the sleeve.

f -V shaped to contact with a correspond ingly formed seat o, as shownin Fig. 4, so

that any slight variation in alinement during descent will be corrected.At the completion of the descent of the frame F &c.,

the curved side of the shoulder s on the 'le-' ver 8 forces saidshoulderinto-engagement with the spring bolt 03, and at the same-time the cam c,acting on :the lower end ofthe lever '17, releases the arm .9 from thelatter, s0 that-upon the withdrawal .of the bolt e, the auxiliary safetyplane 8, s, will be again released and free to adapt itself instantlyto' wind pressure; and to act independently of the niain orfixed planelor. planes as hereinbeforeset forthq fwl .I' i- 1 fiAs hereinbeforeintimated 'I' do not" limit 'myself to the identical formand-Zconstruction ofgdetails and devices herein'shown, the isameflbeing-usedto illustrate the, practical application 'of' my invention, and; beingdesigned to cover iequiia-lent mechanical ex- 'pedients as well asmodlficationswlthin the scope and intent of my invention.

It is to be noted that my auxiliary safety plane and'its connections'areentirely independent of, and do not interfere'with, the

ordinary control ofthe aeroplane; and that under normal fixed conditionsthe auxiliary plane adds to the sum total of the sustainings'urface,while the auxiliary rudder tends to stability of alinement and motion.Furthermore. a single movement of the hand of the aviator is s'uflicientto immediately release the auxiliary safety plane; and a single movementis likewise all that is necessary to reset the'auxiliary plane andrestore it to its normal position. And'if the aviator is care less orincapacitated for any reason, in case of the dangerous lILClHIEItIOIL ofthe aeroplane my automatic release wvill insure" VVhile it may bedesirable under ordinary conditions of use that the auxiliary plane beheld by positive means normally parallel and inproximityito the mainplane surface,

it is also capable of free use and play un-- restrictedly on the mast asautomatic means forycounteracting the effects. .of suddengva riations inpressure or direction of air currents, to facilitate gliding &c., and asa constant safety medium not dependent on manual or mechanical release,in which case a coiled spring w, may be arranged in con-' hat I claim asmy invention and desirev to secure by Letters Patent is, i

1. In combination, an aeroplane, a mast carried by said aeroplane, aframe slidably mounted on said mast, releasable means for locking saidframe in normal position, an

auxiliary plane pivotally mounted onsaid frame, releasable means forlocking saidauxiliary plane parallel to the main-plane surface, and aruddermounted on .said frame. i

2. In combination, an aeroplane, 'a mast carried by said aeroplane, aframe slidably;

mounted on said mast, releasable means for lock ng said frame in normalposition,-an auxiliary plane pivotally mounted on said frame, releasablemeans for locking; saidauxiliary plane parallel to the mainfplanesurface, and a rudder mounted on said frame; said rudder being formed'with.

hinged expandable rear sections, for the purpose described. a a

3. In combination, an aeroplane, a mast carried by said aeroplane, aslidableframe mounted on said mast, an auxiliary plane pivotally mountedon said frame, a rudder mounted on said frame, releasable means forretaining said frame in its normal position, and means for automaticallyreleasing said frame consisting of a spring bolt, a gravity pendulumsupported upon a universal joint formed with lateral arms, and flexiblemeans connecting said arms with said spring'bo-lt whereby when theaeroplane is tilted at a prescribed angle the auxiliary plane will bereleased for the purpose described.

4. In combination, an aeroplane, a mast carried by said aeroplane, aframe slidably mounted on said mast, releasable means for.

locking said frame in normal position, an auxiliary plane pivotallymounted on' said frame, releasable means for locking said auxiliaryplane parallel to the main plane surface, a rudder mounted upon saidframe, and means for turning said auxiliary plane Copies of this patentmay be obtained for into parallelism with the main plane surface afterits release, for the purpose set forth.

'5. In combination, an aeroplane, a mast mounted thereon, a frameslidable on said Inast, releasable means for securing said frame in itsnormal position,an auxiliary plane mounted upon an axis pivotallysupported on said frame, locking arms secured to said axis, and a springbolt and cam releasearranged to act in conjunction with said arms. tolock one while releasing the other, thereby setting the parts in suchmanner that the auxiliary plane may be released by the withdrawing of asingle bolt as and for the purpose set forth. V

6. In combination, an aeroplane, a mast carried thereby extendingsubstantially at right angles to the fixed plane surface, a

frame slidably mounted on said mast, re-- leasable means for lockingsaid frame in its normal position adjacent the fixed plane 'surfaceyanauxiliary plane pivotally mounted'on said frame, and means forautomatically releasing said auxiliary plane axially upon'the release ofthe said frame.

7. Iii-combination, an aeroplane, a mast carried thereby; extendingsubstantially at right angles to the fixed plane surface, a frameslidably mounted on said mast, releasable meansfor lockingsaid frame inits norm'al position'adjace'nt' the fixed plane surface, anauxiliary'plane pivotally mounted on said frame, means for automaticallyreleaslng said auxihary plane axially upon the'releaseof the said frame,and means forbringing said auxiliary plane into par-,

allelism with the fixed plane surface, and automatically locking-it insuch position, for

f ?the purpose-set forth.

8. In combination, an aeroplane, a mast carriedthereby, a frame slidablymounted on said mast, releasable means for locking :said frame in itsnormal position at the bot tom of said mast, an auxiliary planepivotallymounted on said frame, and means for limiting the inclinationof said auxiliary plane when released axially, for thepurpose described.

9. In combination, an aeroplane, a mast carried thereby, a frameslidably mounted on-said mast, releasable means for locking said framein its normal position at the bottom of said mast, an auxiliary planepivotally mounted on said frame, and adjustable means for regulating theprescribed inclination of said auxiliary plane when released forthepurpose described.

PHILIP E. SMITH.

five cents each, by addressing the Commissioner of Patents,

Washington,-D. O. i

